f8d5bf0b1025e84f6e5c807cf9ec15e06c200ec9,trunk/SUAVE/Methods/Geometry/Two_Dimensional/Cross_Section/Airfoil/compute_airfoil_polars.py,,compute_airfoil_polars,#,22

Before Change

            ACD1   = airfoil_aoa[idx_aoa_max_prestall_cd] * Units.degrees     
            
            // Find the point of lowest drag and the CD
            CD_min_loc = np.where(airfoil_cd==min(airfoil_cd))
            ACDmin     = airfoil_aoa[CD_min_loc] * Units.degrees
            CDmin      = airfoil_cd[CD_min_loc]    
            CD0        = airfoil_cd[idx_zero_lift]
            AoA_sweep_radians = AoA_sweep_deg*Units.degrees
            

After Change

            ACD1   = airfoil_aoa[idx_aoa_max_prestall_cd] * Units.degrees     
            
            // Find the point of lowest drag and the CD
            idx_CD_min = np.where(airfoil_cd==min(airfoil_cd))[0][0]
            ACDmin     = airfoil_aoa[idx_CD_min] * Units.degrees
            CDmin      = airfoil_cd[idx_CD_min]    
            AoA_sweep_radians = AoA_sweep_deg*Units.degrees
            
            // Setup data structures for this run

Instances